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A supersonic through-flow fan engine airframe integration studyEngine airframe integration effects are investigated for supersonic through-flow fan engines installed on a Mach 3.20 supersonic cruise vehicle. Six different supersonic through-flow fan engine installations covering the effects of engine size, nacelle contour, nacelle placement, and approximate bypass plume effects are presented. The different supersonic through-flow fan installations are compared with a conventional turbine bypass engine configuration on the same basic airframe. The supersonic through-flow fan engine integrations are shown to be comparable to the turbine bypass engine configuration on the basis of installed nacelle wave drag. The supersonic through-flow fan engine airframe integrated vehicles have superior aerodynamic performance on the basis of maximum lift-to-drag ratio than the turbine bypass engine installation over the entire operating Mach number range from 1.10 to 3.20. When approximate bypass plume modeling is included, the supersonic through-flow fan engine configuration shows even larger improvements over the turbine bypass engine configuration.
Document ID
19900000688
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Barnhart, Paul J. (Sverdrup Technology, Inc. Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1989
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 89-2140
NASA-CR-185140
E-5068
NAS 1.26:185140
Meeting Information
Meeting: Aircraft Design, Systems and Operations Conference
Location: Seattle, Wa
Country: United States
Start Date: July 31, 1989
End Date: August 2, 1989
Sponsors: AHS, ASEE, AIAA
Accession Number
90N10004
Funding Number(s)
PROJECT: RTOP 505-69-61
CONTRACT_GRANT: NAS3-25266
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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